01.1 - Aircraft Design and Integrated System (Basics and Theory)
TILT-DUCT AIRCRAFT WING AERODYNAMIC DESIGN AND OPTIMIZATION BASED ON ADJOINT METHOD
Y.-T. Zhang¹, S.-R. Xu¹, Z.-J. Zheng¹, Y. Zheng¹, Y.-L. Liu¹; ¹Zhejiang University, China
Tilt-duct aircraft, which combines the advantages of high speed and efficiency of fixed wing aircraft and vertical takeoff and landing and hovering of helicopters, is an important trend in the development of future aircraft. Aerodynamic optimization is an important means to enhance the overall performance of tilt-duct aircraft. Compared to traditional aerodynamic optimization methods using finite difference method for gradient calculation, the adjoint method can obtain the gradient of the objective function by solving the equation in one go, which has higher computational efficiency. For tilt-duct wing aerodynamic design optimization problems containing large-scale design variables, the adjoint method has great advantages. Therefore, we use adjoint-based aerodynamic design optimization of tilt-duct aircraft wing, to achieve higher lift-to-drag ratio at desired flight conditions.